Damping element and method for damping rotor blade vibrations, a rotor blade, and a rotor

Abstract

A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine is disclosed. A damping element is guided on a support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with a lower platform area of a rotor blade. A circumferential contact surface is formed by an elevation on the lower platform area, where the circumferential contact surface is a limit stop for a movement of the damping element.

What is claimed is: 
     
       1. A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine, comprising:
 a lower platform area of a rotor blade; 
 a support; 
 a damping element guided on the support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with the lower platform area and wherein the damping element is U-shaped and grips around the support; and 
 a circumferential contact surface formed by an elevation on the lower platform area, wherein the circumferential contact surface is a limit stop for a movement of the damping element; 
 wherein an entirety of the damping system is arranged upstream or downstream from the rotor blade; 
 and wherein an entirety of the damping element is arranged radially under the rotor blade. 
 
     
     
       2. The damping system according to  claim 1 , wherein the turbomachine is an aircraft engine. 
     
     
       3. The damping system according to  claim 1 , wherein the damping element has opposing sliding surfaces and wherein the support has two guide surfaces, and wherein the opposing sliding surfaces are operatively engaged with the two guide surfaces. 
     
     
       4. The damping system according to  claim 1 , wherein the damping system is arranged on an upstream side or a downstream side of the rotor. 
     
     
       5. A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine, comprising:
 a lower platform area of a rotor blade; 
 a support; 
 a damping element guided on the support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with the lower platform area and wherein the damping element is U-shaped and grips around the support; and 
 a circumferential contact surface formed by an elevation on the lower platform area, wherein the circumferential contact surface is a limit stop for a movement of the damping element; 
 wherein the damping element is moveable in a circumferential direction and wherein an entirety of the damping element is arranged radially under the rotor blade. 
 
     
     
       6. A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine, comprising:
 a lower platform area of a rotor blade; 
 a support; 
 a damping element guided on the support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with the lower platform area; and 
 a circumferential contact surface formed by an elevation on the lower platform area, wherein the circumferential contact surface is a limit stop for a movement of the damping element; 
 wherein an entirety of the damping system is arranged upstream or downstream from the rotor blade; 
 wherein an entirety of the damping element is arranged radially under the rotor blade; 
 and wherein the damping element is mounted on the support by a connection element which is guided into a radially extending longitudinal groove of the support. 
 
     
     
       7. A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine, comprising:
 a lower platform area of a rotor blade; 
 a support; 
 a damping element guided on the support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with the lower platform area; 
 a circumferential contact surface formed by an elevation on the lower platform area, wherein the circumferential contact surface is a limit stop for a movement of the damping element; and 
 a frontal contact surface of the rotor blade and wherein the damping element is frictionally contactable with the frontal contact surface; 
 wherein the damping element is U-shaped and grips around the support.